Doosan Heavy Industries & Construction Co., Ltd

Sangshin Elecom Co., Ltd

Jae Bin Lee

Gene Chong

David Ohlschwager

Kibaek Kim

Bryan C Bernier

Seokbeom Kim

Ki Bong Yeo

Hyeong Joon Kim

Young-Soo Lee

Heung Rae Kim

Yunchang Jang

Haneul Kim

An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

Gas turbine inner shroud with abradable surface feature

A turbine blade for a gas turbine engine. The turbine blade includes an airfoil having a tip cavity. The tip cavity has a floor bounded by a wall. A pocket opening is formed in the wall proximate a trailing edge of the turbine blade. A passageway communicates cooling medium from an internal cooling circuit to a cooling hole formed in part through the floor and in part through the trailing edge.

Turbine blade with blade tip ejector

An inner shroud block component for a gas turbine. The inner shroud block has a surface with a plurality of wells formed therein. An array of protuberances extend away from a base surface of each of the wells. The array of protuberances produces convective cooling of the inner shroud block, resulting in increased cooling of the inner shroud block and better part life. The increased cooling capacity also allows the turbine to operate at higher temperatures, which results in additional power generation.

Gas turbine inner shroud with array of protuberances

A gas turbine includes a housing in which combustion gas flows; a rotor section rotatably installed in the housing; and a turbine blade configured to rotate the rotor section by receiving a rotational force from the combustion gas and to be cooled by a cooling fluid flowing in a cooling path, the turbine blade including a tip side provided with tip cooling holes through which a portion of the cooling fluid in the cooling path is discharged from the turbine blade. The tip cooling holes include a first tip cooling hole formed in a pressure surface of the turbine blade, and a second tip cooling hole formed in a suction surface of the turbine blade. The gas turbine can easily maintain a gap between the tip side of the turbine blade and an inner circumferential surface of the housing, preventing degradation of the turbine blade efficiency.

Gas turbine

The present invention relates to a film bulk acoustic wave device and a method of manufacturing the same, wherein comprising an acoustic reflective layer which is formed on a substrate by removing a sacrificial layer on the substrate and becomes an empty space; an oxidation protective film or etch protecting film which is formed in a pattern that divides a resonance region to form the acoustic reflective layer on the sacrificial layer; a thermal oxidation film which is formed by partially thermally oxidizing the sacrificial layer in an electrode region where the oxidation protective film or the etch protecting film is not formed; and a lower electrode, a piezoelectric thin film, and an upper electrode all of which are disposed on the thermal oxide. Further, the present invention is directed to a method of manufacturing the same.

Growing community of inventors

Seoul, South Korea

Jae Bin Lee